Preparation mold and forming method of composite undercarriage component

Abstract

The invention relates to the technical field of composite material forming, and discloses a preparation mold and a forming method of a composite material undercarriage component, and the mold comprises an outer mold assembly, a riser and a center mold; the outer mold assembly comprises a plurality of hard outer molds, the plurality of hard outer molds are detachably connected, and a closed shell structure is defined by the plurality of hard outer molds; a plurality of risers are arranged, the plurality of risers are arranged on the shell structure at intervals, and the risers are connected with a resin injection source or functional equipment; the central mold is used for providing an inner side molded surface for the hollow undercarriage component; and the outer wall of the central mold and the inner wall of the outer mold combination body are encircled to form a mold cavity for forming the undercarriage component. The large-size, hollow and special-shaped composite undercarriage component can be integrally formed and prepared, the mechanical property and the size precision of the component are remarkably improved, and the yield is increased.

Description

Technical Field

[0001] This invention relates to the field of composite material molding technology, and in particular to a mold and molding method for preparing composite material landing gear components. Background Technology

[0002] As a critical load-bearing component of aircraft, the landing gear withstands enormous impact loads and complex stresses during takeoff and landing. Applying composite materials to main load-bearing structures such as landing gear is currently a research hotspot in the aerospace manufacturing field. Fiber-reinforced resin matrix composites are widely used in aerospace structures due to their high specific strength, high specific stiffness, fatigue resistance, corrosion resistance, and excellent designability. For unmanned aerial vehicles (UAVs), using composite materials to manufacture landing gear can significantly reduce overall weight and improve payload capacity and range.

[0003] However, landing gear components typically possess large dimensions, high aspect ratios, hollow structures, and irregular geometric shapes, and require extremely high load-bearing capacity. Existing composite material molding processes suffer from the following significant drawbacks when manufacturing such complex components: The first challenge is controlling resin flow. Traditional liquid molding processes typically employ single-point or a few injection points. For large, complex landing gear components, the resin flow path within the mold cavity becomes exceptionally long and tortuous. This long resin flow path easily triggers a series of predictable manufacturing defects. The viscosity and curing kinetics of the resin determine its limited process window time. If the resin injection time exceeds this window, it begins to gel, its viscosity increases sharply, preventing further flow and resulting in dry spots that are not fully impregnated with resin in areas far from the injection point. Furthermore, the resin instinctively chooses the path of least resistance during flow, a phenomenon known as the edge-seeking effect. This causes the resin to flow rapidly along the mold edge or in areas with higher permeability, while dense fibrous areas are bypassed, creating resin-poor regions. These defects ultimately lead to numerous pores, uneven fiber volume fraction, and inconsistent thickness within the cured component, severely weakening its mechanical properties and preventing it from meeting the stringent performance requirements of load-bearing structures such as landing gear.

[0004] Secondly, there is the challenge of demolding in hollow structure molding. Manufacturing hollow components requires the use of mandrels to form their internal cavities. If traditional rigid mandrels (such as steel or aluminum) are used, removing the mandrel after curing becomes extremely difficult for components with complex internal curved surfaces or recessed features. Forced demolding often requires applying enormous external force, which can easily cause irreversible damage to valuable composite material components, or even directly lead to product scrap.

[0005] In the prior art, in order to avoid the above-mentioned defects, the common method for molding large-size complex structures of composite materials is to separately cure and mold the complex structures, and then use a co-bonding process to bond them together. The process is as follows: the structural units of the composite material skin and rib parts are separately cured and molded, and then positioned, assembled and bonded for secondary curing. This molding method can reduce the workload of mold processing, but the bonding method will cause the fibers at the joints to break, affecting the mechanical properties of the overall structure.

[0006] To address this, a mold and molding method for preparing composite material landing gear components are proposed. Summary of the Invention

[0007] The purpose of this invention is to provide a mold and molding method for preparing composite material landing gear components, aiming to solve or improve at least one of the above-mentioned technical problems.

[0008] To achieve the above objectives, the present invention provides the following solution: The present invention provides a mold for manufacturing composite material landing gear components, comprising: An outer mold assembly, comprising a plurality of rigid outer molds, wherein the plurality of rigid outer molds are detachably connected and together form a closed shell structure; A riser is provided, and the riser is installed at intervals on the shell structure. The riser is connected to a resin injection source or a functional device. A central mold, which is used to provide an inner profile for a hollow landing gear component; The outer wall of the central mold and the inner wall of the outer mold assembly together form a cavity for molding the lifting and lowering structure component.

[0009] According to the present invention, a mold for preparing a composite material landing gear component is provided, wherein the material of the central mold is any one or more of foam, rubber, wooden pads, and airbags.

[0010] According to the present invention, a mold for preparing a composite material landing frame component is provided, wherein a plurality of risers are spaced apart and installed on the outer top wall of the shell structure.

[0011] According to the present invention, a mold for preparing a composite material landing gear component is provided, wherein the rigid outer mold is made of metal; two adjacent rigid outer molds are detachably connected by bolts, and a sealing strip is installed between two adjacent rigid outer molds.

[0012] The present invention also provides a method for molding a composite material landing gear component, comprising the following steps: Step 1: Mold preparation; Step 2: Prepare the fiber dry cloth and resin. Determine the layup direction and number of layers of the fiber dry cloth according to the preset component structure, and cut the fiber dry cloth. Step 3: Lay the cut fiber dry cloth on the surface of the central mold to form a fiber preform, and place the fiber preform into the cavity formed by several rigid outer molds; Step 4: Close several rigid outer molds and seal them; Step 5: Switch each riser to the resin injection source or functional device through the preset program to inject liquid resin into the cavity and impregnate the fiber preform. Step 6: Under preset temperature and pressure conditions, heat and cure the resin-impregnated fiber preform to form a composite material lifting frame component; Step 7: After cooling, open the outer mold assembly to complete demolding, obtain the composite material lifting frame component, and perform post-processing.

[0013] According to the molding method of a composite material landing frame component provided by the present invention, the specific operation of step five is as follows: in the initial stage, resin is injected through the riser located in the center, and the resin flow front is monitored through the window or sensor. When the resin flows to the predetermined position at the end of the cavity, the control system automatically switches the valve state so that the riser at the predetermined position at the end is injected with resin. The fiber preform is fully impregnated until pure resin flows out of all the vents of the risers without any bubbles are generated.

[0014] According to the molding method of a composite material landing frame component provided by the present invention, the specific operation of step one is as follows: cleaning the molding surfaces of the rigid outer mold and the central mold, and spraying a water-based release agent. The fiber dry filament cloth is made of unidirectional cloth or woven cloth, and the fiber of the fiber dry filament cloth is any one or more of carbon fiber, glass fiber, and aramid.

[0015] According to the molding method of a composite material landing frame component provided by the present invention, the specific operation of step six is ​​as follows: transferring the sealed and complete outer mold assembly to an oven, heating and curing the resin-impregnated fiber preform, and then cooling it in the oven to form a composite material landing frame component.

[0016] According to the molding method of a composite material landing frame component provided by the present invention, the specific operation of step seven is as follows: after the mold cools to room temperature, the outer mold assembly is disassembled, the rigid outer mold is separated and removed to obtain the composite material landing frame component, and the molded composite material landing frame component is further processed.

[0017] The present invention discloses the following technical effects: The present invention uses several rigid outer molds to form a closed shell structure, the inner surfaces of which together constitute the outer forming surface of the lifting frame component. The rigid outer molds ensure the smoothness and dimensional tolerance of the outer surface of the component. The outer surface of the soft inner mold constitutes the inner forming surface of the lifting frame component. The foam core mold is not removed and is used to combine with the soft inner mold to define the internal hollow open structure of the lifting frame component. The combination structure of the outer mold assembly and the central mold can form a complex hollow structure in one piece, avoiding the fiber discontinuity problem caused by traditional split manufacturing and re-gluing. It ensures the structural integrity of the component and the continuous transfer of mechanical properties, and can realize the precise construction of complex cavities and convenient demolding. This invention employs liquid molding technology, laying a fiber preform within a mold cavity and using several risers that alternately switch between resin injection and venting functions. This allows for staged and multi-point control of resin flow and impregnation, breaking down the long impregnation process into multiple controllable short processes. It actively guides the resin flow front, effectively solving the edge-tending effect, shortening the injection time, ensuring uniform and complete resin impregnation of the fiber preform, significantly reducing porosity, and finally curing under controlled temperature and pressure conditions. This allows for the integrated molding of large-size, hollow, and irregularly shaped composite landing gear components, significantly improving the mechanical properties and dimensional accuracy of the components. It is suitable for manufacturing key load-bearing components of high-performance aircraft, increasing yield. The central mold of this invention applies uniform molding pressure to the fiber preform, effectively suppressing fiber wrinkles and ensuring the stability of the inner cavity shape and dimensional accuracy. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 An exploded view of the mold used in this invention; Figure 2 This is a schematic diagram of the landing gear structure in this invention; Figure 3 This is a schematic diagram of the structure of the outer mold assembly in this invention; Figure 4 This is a schematic diagram of the combined central mold used in Embodiment 1 of the present invention.

[0020] Among them, 1. rigid outer mold; 2. central mold; 21. foam core mold; 22. soft inner mold; 221. rubber air bladder; 222. heat shrinkable foam filler; 3. fiber preform; 4. cavity; 5. riser; 100. lifting frame component; 200. outer mold assembly. Detailed Implementation

[0021] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0023] Example 1 Reference Figures 1-4 This invention provides a mold for manufacturing composite landing gear components, comprising: The outer mold assembly 200 includes several rigid outer molds 1, which are detachably connected and enclose a closed shell structure. Riser 5, several risers 5 are provided, several risers 5 are installed at intervals on the shell structure, and risers 5 are connected to resin injection source or functional equipment; Center mold 2, center mold 2 is used to provide the inner profile for the hollow landing gear component; The outer wall of the central mold 2 and the inner wall of the outer mold assembly 200 together form a cavity 4 for molding the landing frame component 100; the structure of the cavity 4 is exactly the same as the shape of the fiber preform 3 and the molding landing frame component 100. With this configuration, the several rigid outer molds 1 of the present invention enclose a closed shell structure, and their inner surfaces together constitute the outer forming surface of the lifting frame component 100. The rigid outer molds ensure the smoothness and dimensional tolerance of the outer surface of the component. The combination structure of the outer mold assembly and the central mold 2 can form a complex hollow structure that is integrally formed in one go, avoiding the fiber discontinuity problem caused by traditional split manufacturing and re-gluing, ensuring the structural integrity of the component and the continuous transmission of mechanical properties, and enabling the precise construction of complex cavities and convenient demolding. This invention employs liquid molding technology, laying a fiber preform 3 within a mold cavity 4. Several risers 5 alternately switch between resin injection and venting functions, thereby controlling the resin flow and impregnation in stages and at multiple points. This breaks down the long impregnation process into multiple controllable short processes, actively guiding the resin flow front, effectively solving the edge-tending effect, shortening the injection time, ensuring uniform and complete resin impregnation of the fiber preform 3, significantly reducing porosity, and finally curing under controlled temperature and pressure conditions. This allows for the integrated molding of large-size, hollow, irregularly shaped composite landing gear components 100, significantly improving the mechanical properties and dimensional accuracy of the components. It is suitable for manufacturing key load-bearing components of high-performance aircraft, increasing the yield rate. The central mold 2 of the present invention applies uniform molding pressure to the fiber preform 3, effectively suppressing fiber wrinkles and ensuring the stability of the inner cavity shape and dimensional accuracy.

[0024] Further optimization of the scheme: the material of the central mold 2 can be any one or more of foam, rubber, wooden pads, and airbags.

[0025] Further optimization of the design: the central mold 2 includes a soft inner mold 22 and a foam core mold 21. Both the soft inner mold 22 and the foam core mold 21 are located within the shell structure. The foam core mold 21 is located on one side of the soft inner mold 22. The soft inner mold 22 is filled with heat-shrinkable foam filler 222. A rubber airbag 221 is fitted on the outer surface of the soft inner mold 22. The outer wall of the soft inner mold 22, the outer wall of the foam core mold 21, and the inner wall of the outer mold assembly 200 together form a cavity 4 for molding the lifting frame component 100. The heat-shrinkable foam filler 222 shrinks in volume during the molding heating process to form a demolding gap. Rubber airbag 221 is made of high-strength heat-resistant silicone or heat-cured rubber; The outer surface of the soft inner mold 222 forms the inner molding surface of the landing frame component 100. The foam core mold 21 is not removed and is used to define the internal hollow open structure of the landing frame component 100 when combined with the soft inner mold 222. The combination structure of the outer mold assembly and the central mold 2 can form a complex hollow structure that is integrally molded in one go, avoiding the fiber discontinuity problem caused by traditional split manufacturing and re-gluing. This ensures the structural integrity of the component and the continuous transfer of mechanical properties, and enables the precise construction of complex cavities and convenient demolding. During the molding process, the rubber air bladder 221 of the soft inner mold 222 applies uniform molding pressure to the fiber preform 3 through internal inflation, effectively suppressing fiber wrinkles and ensuring the stability and dimensional accuracy of the inner cavity shape. The heat-shrinkable foam filler 222 filled in the soft inner mold 222 shrinks in volume when cured and heated, automatically forming a demolding gap, so that the soft inner mold 222 can be easily and completely removed from the complex inner cavity, completely avoiding component damage caused by forced demolding and improving the yield.

[0026] Further optimization of the scheme: the foam core mold 21 is made of polymethacrylamide foam. The foam core mold 21 is not removed after molding and serves as a permanent core mold. The foam core mold 21 is made of polymethacrylamide foam with a service temperature higher than the resin molding temperature and the component operating temperature.

[0027] In a further optimized design, several risers 5 are installed at intervals on the outer top wall of the shell structure. In this embodiment, there are five risers 5, which are evenly or as needed distributed on the outer top wall of the shell structure to achieve multi-point and zoned control of resin flow.

[0028] Further optimization of the design: the rigid outer mold 1 is made of metal; two adjacent rigid outer molds 1 are detachably connected by bolts, and a sealing strip is installed between two adjacent rigid outer molds 1 to ensure sealing under high temperature and high pressure; positioning pins and guide groove structures are used for precise positioning, and bolts are used for fastening installation and disassembly.

[0029] The present invention also provides a method for molding a composite material landing gear component, comprising the following steps: Step 1: Mold preparation; Step 2: Prepare the fiber dry cloth and resin. Determine the layup direction and number of layers of the fiber dry cloth according to the preset component structure, and cut the fiber dry cloth. Step 3: Lay the cut fiber dry cloth on the surface of the central mold 2 to form a fiber preform 3, and place the fiber preform 3 into the cavity 4 formed by several rigid outer molds 1. Step 4: Close several rigid outer molds 1 and seal them; Step 5: Switch each riser 5 to the resin injection source or functional device through a preset program to inject liquid resin into the cavity 4 and impregnate the fiber preform 3; in this embodiment, the functional device is a vacuum source; Step 6: Under preset temperature and pressure conditions, heat and cure the resin-impregnated fiber preform 3 to form a composite material landing frame component 100. Step 7: After cooling, open the outer mold assembly 200 to complete demolding, obtain the composite material landing frame component 100, and perform post-processing.

[0030] Further optimize the scheme. The specific operation of step five is as follows: In the initial stage, resin is injected through the riser 5 located in the center, and the other risers 5 are connected to the vacuum system to pump the vacuum degree in the cavity 4 to -0.095MPa; the resin flow front is monitored through the window or sensor. When the resin flows to the predetermined position at the end of the cavity 4, the control system automatically switches the valve state so that the riser 5 at the predetermined position at the end is injected with resin. When pure resin flows out of all the vents of risers 5 and no bubbles are generated, it indicates that the fiber preform 3 has been completely impregnated. During the process of injecting liquid resin into the cavity 4, compressed air at 0.2 MPa is continuously introduced into the rubber air bladder 221 of the soft inner mold 222.

[0031] Further optimize the scheme. The specific operation of step one is as follows: clean the molding surfaces of the hard outer mold 1 and the central mold 2, and spray water-based release agent on the surfaces of the hard outer mold 1 and the soft inner mold 22. The fiber dry filament cloth is made of unidirectional cloth or woven cloth. The fiber of the fiber dry filament cloth is any one or more of carbon fiber, glass fiber, and aramid. The fiber preform can be made by layering and winding a single layer of fiber cloth or by weaving or woven methods. Further optimize the scheme. The specific operation of step six is ​​as follows: transfer the sealed and complete outer mold assembly 200 into an oven. The oven temperature is raised from room temperature to 90℃ to 130℃ at a rate of 1.5℃ / min to 3℃ / min, and held at 90℃ to 130℃ for 120 minutes to 180 minutes to heat and cure the resin-impregnated fiber preform 3. Then, it is cooled in the oven to form the composite material lifting frame component 100.

[0032] Further optimize the scheme. The specific operation of step seven is as follows: After the mold cools to room temperature, disassemble the outer mold assembly 200, separate and remove the hard outer mold 1, and completely remove the soft inner mold 22 to obtain the lifting frame component 100 of the composite material. Then, perform subsequent processing on the molded lifting frame component 100 of the composite material. Subsequent processing includes cutting both ends to ensure end face quality and structural integrity, surface grinding to remove burrs and flash, and precise positioning and drilling at the designed locations for the installation of components such as axles.

[0033] In this embodiment, T300 grade carbon fiber plain weave fabric is prepared as the fiber dryer cloth, and bisphenol A type epoxy resin system is used; based on the mechanical performance requirements of the component, the fiber dryer cloth adopts [0 / 90 / 45 / -45]. 6s The quasi-isotropic layup scheme is used to lay up a total of 48 layers, and the fiber dry cloth is precisely cut accordingly. The fiber preform 3 formed by the 48 layers of fiber dry cloth is carefully laid on the surface of the central mold 2 composed of soft inner mold 222 and foam core mold 21 in strict accordance with the layup sequence and direction. In this embodiment, the curing process raises the temperature from room temperature to 120°C at a rate of 2°C / min, holds at 120°C for 120 minutes, and then cools with the furnace.

[0034] Example 2 This embodiment demonstrates the fabrication of landing gear components under different process parameters to illustrate the process adaptability of the present invention.

[0035] 1. Raw materials and layup: M30 grade high-strength, high-modulus carbon fiber twill fabric is used, and the layup design is adjusted to [0 / 45 / 90 / -45]. 8s The total number of layers has been increased to 64 in order to achieve higher mechanical properties.

[0036] 2. Resin Injection Strategy: A two-stage injection method is adopted to optimize efficiency. First, resin is injected under pressure through two risers 5 at one end of the component connected to the RTM device; when the resin flows to about 2 / 3 of the total length of the mold, the injection is switched to all five risers 5 simultaneously, thereby shortening the total injection time.

[0037] The other steps in this embodiment are the same as in Embodiment 1. This demonstrates that the present invention can flexibly adapt to the requirements of different molding processes, material systems, and performance indicators by adjusting key process parameters.

[0038] Example 3 This embodiment illustrates the application of the present invention in the manufacture of small, high-precision composite material components.

[0039] 1. Mold Material and Structure Optimization: The rigid outer mold 1 is made of pre-hardened mold steel P20 to achieve better surface finish and dimensional stability. The central mold 2 is made entirely of rigid foam to better reproduce the fine and complex internal cavity contours; the surface of the central mold 2 is not coated with release agent and is not removed after molding.

[0040] 2. Curing Strategy Adjustment: A low-temperature, long-duration curing scheme is adopted, with the molding temperature controlled at 90℃, the heating rate set at 1.5℃ / min, and the holding time extended to 180 minutes. This strategy helps reduce internal residual stress during the curing process, thereby improving the dimensional stability and shape accuracy of the component.

[0041] The remaining main steps of this embodiment are consistent with those of Embodiment 1. This demonstrates that the present invention, through the refined design of mold materials and curing processes, is also applicable to the manufacture of small, complex components with extremely high requirements for dimensional accuracy and internal quality.

[0042] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0043] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively describe all embodiments here. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the claims of the present invention.

Claims

1. A mold for manufacturing a composite material landing gear component, characterized in that, include: The outer mold assembly (200) includes a plurality of rigid outer molds (1), which are detachably connected and enclosed to form a closed shell structure. Riser (5), a plurality of risers (5) are provided, a plurality of risers (5) are installed at intervals on the shell structure, and the risers (5) are connected to a resin injection source or a functional device; A central mold (2) is used to provide an inner profile for a hollow landing gear component; The outer wall of the central mold (2) and the inner wall of the outer mold assembly (200) together form a cavity (4) for molding the landing frame component (100).

2. The mold for manufacturing composite material landing gear components according to claim 1, characterized in that: The material of the central mold (2) is any one or more of foam, rubber, wooden pads, and airbags.

3. The mold for manufacturing composite material landing gear components according to claim 1, characterized in that: Several of the risers (5) are installed at intervals on the outer top wall of the shell structure.

4. The mold for manufacturing composite material landing gear components according to claim 1, characterized in that: The rigid outer mold (1) is made of metal; two adjacent rigid outer molds (1) are detachably connected by bolts, and a sealing strip is installed between two adjacent rigid outer molds (1).

5. A molding method for a composite material landing gear component, based on the mold for preparing the composite material landing gear component according to any one of claims 1-4, characterized in that, Includes the following steps: Step 1: Mold preparation; Step 2: Prepare the fiber dry cloth and resin. Determine the layup direction and number of layers of the fiber dry cloth according to the preset component structure, and cut the fiber dry cloth. Step 3: Lay the cut fiber dry cloth on the surface of the central mold (2) to form a fiber preform (3), and place the fiber preform (3) into the cavity (4) formed by several rigid outer molds (1); Step 4: Close several rigid outer molds (1) and seal them; Step 5: Switch each riser (5) to the resin injection source or functional device through the preset program, inject liquid resin into the cavity (4), and impregnate the fiber preform (3). Step 6: Under preset temperature and pressure conditions, heat and cure the resin-impregnated fiber preform (3) to form a composite material landing frame component (100). Step 7: After cooling, open the outer mold assembly (200) to complete demolding, obtain the composite material landing frame component (100), and perform post-processing.

6. The molding method for the composite material landing gear component according to claim 5, characterized in that: The specific operation of step five is as follows: In the initial stage, resin is injected through the riser (5) located in the center. The resin flow front is monitored through the window or sensor. When the resin flows to the predetermined position at the end of the cavity (4), the control system automatically switches the valve state so that the riser (5) at the predetermined position at the end is injected with resin. The fiber preform (3) was fully impregnated until pure resin flowed out of the vents of all risers (5) and no bubbles were generated.

7. The molding method for the composite material landing gear component according to claim 5, characterized in that: The specific operation of step one is as follows: clean the molding surfaces of the hard outer mold (1) and the central mold (2), and spray water-based release agent; The fiber dry filament cloth is made of unidirectional cloth or woven cloth, and the fiber of the fiber dry filament cloth is any one or more of carbon fiber, glass fiber, and aramid.

8. The molding method for the composite material landing gear component according to claim 5, characterized in that: The specific operation of step six is ​​as follows: the sealed and complete outer mold assembly (200) is transferred to the oven, the resin-impregnated fiber preform (3) is heated and cured, and then cooled with the oven to form a composite material lifting frame component (100).

9. The molding method for the composite material landing gear component according to claim 5, characterized in that: The specific operation of step seven is as follows: after the mold cools to room temperature, disassemble the outer mold assembly (200), separate and remove the hard outer mold (1) to obtain the landing frame component (100) of the composite material, and perform subsequent processing on the formed landing frame component (100) of the composite material.

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